Dynamic Systems Analysis - Glenn Research Center | NASA€¦ · · 2013-12-04National Aeronautics...
Transcript of Dynamic Systems Analysis - Glenn Research Center | NASA€¦ · · 2013-12-04National Aeronautics...
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National Aeronautics and Space Administration
www.nasa.gov
Dynamic Systems Analysis
4th Propulsion Control and Diagnostics Workshop
Ohio Aerospace Institute (OAI)
Cleveland, OH
December 11-12, 2013
1
Jeffrey Csank
NASA Glenn Research Center
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National Aeronautics and Space Administration
www.nasa.gov
Team Members
• Jonathan Seidel, NASA Glenn Research Center/RTM
• Jeffrey Chin, NASA Glenn Research Center/RTM
• Alicia Zinnecker, N&R Engineering
• Georgia Institute of Technology
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National Aeronautics and Space Administration
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Outline
• Preliminary Engine Design
• Systems Analysis
• Tool for Turbine Engine Closed-loop Transient
Analysis (TTECTrA)
• Dynamic Systems Analysis
• Conclusion
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National Aeronautics and Space Administration
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Preliminary Engine Design
• Huge commitments are made
based on results
• A completely new engine is
relatively rare
• Most programs focus on
derivative engines
4
Weight
Performance
Scaling
Mission
Cycle
Configuration
Component
Design
Component
Test
Performance
Manufacture
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National Aeronautics and Space Administration
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Systems Analysis
• Complex process that involves system-level
simulations to evaluate system-level
performance, weight, and cost (optimize system,
compromise component)
• Focus on steady-state design cycle performance
• Dynamic considerations
and issues are
incorporated through the
use of operating margins
– Stall margin
5
Corrected Flow (Wc)
Pre
ssu
re R
atio
(P
R)
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National Aeronautics and Space Administration
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Tool for Turbine Engine Closed-loop
Transient Analysis (TTECTrA)
• Capable of automatically designing a controller
• Easily integrates with users engine model in
MATLAB/Simulink environment
• Provide an estimate of the closed-loop transient
performance/capability of a conceptual engine design
• Requirements:
– MATLAB®/Simulink® (Release R2012b or later)
• MATLAB® Version 8.0 (R2012b)
• Simulink® Version 8.0 (R2012b)
• Control Systems Toolbox® Version 9.4 (R2012b)
– Engine Model compatible with Simulink
– State space linear model in MATLAB
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National Aeronautics and Space Administration
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TTECTrA Architecture
• TTECTrA software automatically designs:
– Set Point
– Set Point Controller
– Limit Controller
• Simulates different thrust profiles
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User Model Set Point
Controller
Limit
Controller
Engine
Sensors
Selecto
r Lo
gic
Desired
Thrust
Set
Point
Actuator
Feedback
Error
Fuel
Flow Engine
Outputs Set Point
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National Aeronautics and Space Administration
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TTECTrA - Set Point Function
• Flight condition (altitude, Mach, temperature)
• Define set point bounds and number of breakpoints
– Fuel flow
– Thrust
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0 1 2 3 4 5
x 104
1000
1500
2000
2500
3000
3500
4000
4500
Close figure to accept setpointsLeave figure open and use GUI to recalculate
Corrected Thrust (lbf)
Con
tro
l V
ari
ab
le
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National Aeronautics and Space Administration
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TTECTrA – Set Point Controller
• Bandwidth (Hz)
• Phase Margin
• Feedback filter (Hz)
• Throttle Filter (Hz)
9
-50
0
50
100
150
Mag
nitud
e (
dB
)
100
-180
-135
-90
-45
0
Pha
se
(d
eg
)
Bode Diagram
Frequency (rad/s)
Plant
Loop Gain
-10 0 10 20 30 40-10
-5
0
5
10Root Locus
Real Axis (seconds -1)
Imag
inary
Axi
s (
seco
nd
s-1)
0 2 4 60
0.5
1
1.5
Time, s
Con
trol
Vari
able
LM
Pre-Filter
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TTECTrA – Limit Controller
• Acceleration Minimum Surge Margin (HPC)
– Ncdot vs NcR25
• Deceleration Minimum Surge Margin (LPC)
– Wf/Ps3
10
7000 8000 9000 10000 11000 120000
200
400
600
800
1000
1200
1400
Corrected core speed (rpm)
Core
acce
lera
tion
(rp
m/s
ec)
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User Model
TTECTrA - Selector Logic / Actuator
• Selector Logic (Min/Max scheme)
– Min (Set Point, Acceleration)
– Max (Min, Deceleration)
• Actuators
– Currently only models fuel flow
– First order filter
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Engine
Sensors
Selecto
r Lo
gic
Desired
Thrust Set Point
Actuator
Feedback
Error
Fuel
Flow Engine
Outputs
Set Point Set Point
Controller
Limit
Controller
Actuator
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National Aeronautics and Space Administration
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Commercial Modular Aero Propulsion
System Simulator 40,000 (C-MAPSS40k)
• 40,000 Lb Thrust Class High Bypass Turbofan
Engine Simulation
• Matlab/Simulink Environment
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• Publically
available
• Realistic controller
• Realistic surge
margin
calculations
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National Aeronautics and Space Administration
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Burst and Chop Thrust Profile
• Idle (14% of max thrust) to Take-off thrust profile to test
the TTECTrA controller
• Compare the thrust response to the Federal Aviation
Administrations (FAA) Federal Aviation Regulation
(FAR) Part 33, Section 33.73(b)
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0 10 20 30 40 500
2
4
6x 10
4
Time, s
Thru
st
0 10 20 30 40 501
1.5
2
Time, s
Con
tro
l V
ari
ab
le
Dmd
Fdbk
10 12 14 16 180
1
2
3
4
5x 10
4
Time, s
Thru
st
Dmd
Fdbk
95% Max
5 s
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Burst and Chop Thrust Profile
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0 10 20 30 40 5010
20
30
40
50
HP
C S
M, %
Time, s
6000 8000 10000 12000-1000
-500
0
500
1000
1500
2000
Nc
dot
NcR25
0 10 20 30 40 5010
20
30
40
50
60
LP
C S
M, %
Time, s
0 10 20 30 40 500
0.002
0.004
0.006
0.008
0.01
0.012
Wf/P
s3
Time, s
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Engine Deterioration
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0 20 40 6010
20
30
40
50
Time, s
HP
C S
M, %
0 20 40 6010
20
30
40
50
60
Time, s
LP
C S
M
0 20 40 601
1.2
1.4
1.6
1.8
Time, s
Con
tro
l V
ari
ab
le
0 20 40 600
1
2
3
4
5x 10
4
Time, s
Thru
st, lbf
New
EOL
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The Benefit of TTECTrA
Stack %
Uncertainty 11
Reynolds Number 2
Distortion 4
Tip Clearances 1.5
Deterioration 1.5
Random 2
Transient Allowance 12
Total 23
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Do we have enough margin? Too much margin?
Corrected Flow (Wc)
Pre
ssu
re R
atio
(P
R)
Uncertainty
SA
DSA
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National Aeronautics and Space Administration
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The Benefit of TTECTrA
• Combustor Stability
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• Turbine life
• Low Pressure
Compressor
NcR25, rpm
Ps3
R, p
si
SA
DSA
Corrected Flow (Wc)
Pre
ssu
re R
atio
(P
R)
SA
DSA
Nc, rpm
T40
, R
SA
DSA
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Future Work
• NPSS Model in Simulink
– Georgia Institute of Technology
• Integrate TTECTrA with the NPSS Simulink model
– NASA/RHC
• Integrate TTECTrA/NPSS Simulink with a larger
systems analysis optimization algorithm
– NASA/RHC and NASA/RTM
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Conclusion
• Dynamic systems analysis:
– Enables engine transient performance to be accounted for in
the optimization of the engine design and early in the
preliminary design of turbine engines.
– Allows trading of overly conservative surge margin for better
performance through system redesign (or opline).
• Developed the Tool for Turbine Engine Closed-loop
Transient Analysis (TTECTrA)
– Capable of automatically designing a controller at a single
flight condition.
– Easily integrates with users engine model in
MATLAB/Simulink environment.
– Open source
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Questions?
20
Thank you